Project Mercury Familiarization Manual 20 Dec 1962

8/8/2019 Project Mercury Familiarization Manual 20 Dec 1962

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PROJECTMERCURYFAMILIARIZATION

MANUALNASA

M_LNNE D SATELLITE SPACE Cl_AFTON_ DAY MISS]ION

1 DECEMBER 1962

MCDONNELL

AIR FORCE, Mendle Press, Inc. 12/12/62 900 (McDonnell A/C Corp.)


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_4s 4oc_zent is applicable to Spacecraft No. 20 and its one-day o_bital mission an_ supersedes basic SEER 10_-18_ dated 1 JuneI_:_ )ga_ _114_e Spacecraft 18-Orblt Co_aticn. _hlsdoc,-_nt covers Spacecraft No. 20 as delivere_ but does not tn-cluae changes generated after delivery.

The purpose of This _mnent is tO present a clear operatio--1descrlptic_ of the spacecraft systems _ laa_or c_-ponents. A can-parlsom between _-/ompcments _11,_. in previous spacecraftaml those Installea in Spacecraft No. 20 can be made by the use of

earlier issues of +.l_s _ocw_ent. Spacecraft r,--_ered2, 3, 4, 5_6, 7, Ii, an_ 14 are covered in the i Febx.,a_yi_i issue ofi0_ Revised i August 1961. Spacecraft n,_re_ 9, 13, 16, 18 and19 are covered in the 1 November 1961 issue of _R i04-3 Revised1 February 1962.


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SECTION INDEX.

SECTION IINTRODUCTION

SECTION IICABIN

SECTION IIIMAJOR STRUCTURAL ASSEMBLIES

SECTION IVEN VIRO NMEN TA L CO NTRO L S YS TEMSECT ION VSTAB IL IZATION CONTROL SYSTEMSECTION V l

S EQUEN CE S YS TEM, LA UN CH,RETRO GRA DE O R A BO RT.SECTION VII.

_SEQUENCESYSTEM, LANDING THROUGH.RECOVERYSECTION VIII

ESCAPE AND JETTISON ROCKET SYSTEMSECTION IX

POS IGRADE RO CKET SYSTEMSECTION X

.RETROGRADE ROCKET SYS TEMSECTION Xl

ELECTRICAL POWER AND INTERIO R LIGHTING S YS TEMSSECTION Xll

CC_MMUNICATION SYSTEMSECTION XlII

NAV IGAT IONAL A IDSS ECTIO N XlV

IN STRUMEN TA TIO N SYS TEMS


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SECTION I

INTRODUCTION

TABLE OF CONTENTSTITLE PAGDescription................ .................................. .1-3Cabin ........................................................ ,1-5Major Structural Assemblies .................... .1-5Environmental Control System ................. I-5Stabilization Control System...................... 1-5Sequence System....................................... I-6Rocket Motors ............................................ 1-6ElectricalPower AndInterior Lighting System ............................. 1-6

% Communication System........................... .1-6Navigational Aids ...................................... 1-8Instrumentation System............................. .1-8

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SPIKE

P YLO N JE 1T IS ON R OC KE T

SPACECRAFT ADAPTER

RETRO ROCKET ANDPOSIGRADE ROCKETS

ATLAS "D" MISSILE

FM18-43

Figure 1-1 Spacecraft Prelaunch Configuration

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I. I_ZROIUCTION TO PROJECT M_CURY

z.,z. immmzm zoMercury Spacecraft deserlbe_ in this manual is des_ for a

Qne-_sy earth-orbiting mtsslcn. _e ._eatc= is an extenstca of _three-orbit an_ six-_btt flights of the Mercury vehicle.

_e 0he-Day Spacecraf_ is s_.41-- tO the earller e_tlons:eas_t_ 7_ inches in _Ltmster at the v_lest part of the spscecra_tand 115 inches (See Figmre 1-2) fro: the heat shield to the ena of therecovery eyl_r. _he spacecraft shape res_les a _mmeate4 co_etopped by a short cylinder --_ retopped by a shorter truncat_L cone.2he first c_ contains the astr_ut and his m_pcrting s__-_-, theCyl-_-_l,_'r contain- the recovery al4s and parachutes fc_ la._4._, the _cc_1co_e Is the 8n_-- falr_ which cc_$_L_s T_e bicone --_emma 8n_ hu_isonsenslng elements plus the drogue chute.

Str_ling the _t_-, f_ng is a trlm_ular-_mpe_ trusvork ofsteel tublng fca_In_ the escape tower. Two soll_ propellaDt rookets aremounted on top of the tower: one escape, _ _ettlscn.

At the base of _ spacecraft, a heat sbtel_ of shlatl_ _lass f_bercomposition 10 a_tached to _he Impact _ skirt. _ _,'_.le_e as_mb_i_shel_ securely to _ spacecraft until I_. _* re_ rocketmotor pack is attaehea to the heat ._lel_ end is _ettlsoned after retro-fire.

first cone Is a _ouble-wall structure, the inner wall forming apressure vessel (the eshin) and the outer shell for_ a heat -_fel_.

_he following paragraphs briefly describe the material covere_ in

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_a. < _

_ z_ _._ _8o u_8: _

__"_FMI 8-149

Figure 6-5 Escape Before Liftoff Before Umbilical Disconnect

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Micro-Second T_-_ Delay Relay contacts and through tb_ m_ssile to theMayday Relays. In the event the spacecraft must be aborted on thelaunch pad and the m_ssile is unable to tran_tt the hardline abortsignal, there is one other method which may be selected. UmbilicalPins _ and 45 are abort wired and transmit 28 V power from the blockhouse to the spacecrai_'s Ground Co.w-nd Abort Signal Latching Relayenergizing a na locking in the relay. _rough this energized relay space-craft 28 V Squib Arm Bus power is transmitted to the pole of the GroundTest Umbilical Relay; however, power will not continue through this relayuntil the relay is de-energized. _e only way the relay may be de-energized is by ejecting the ,m_ilical. _herefore, if this abortmethod is required to be used, it woula be necessary for the blockhouse conducter to select the Abort Switch (power to pins _ and _5)and within mi_l_seco_ds thereafter the ,w_ilical is ejected. After theMayday Relays are energized, the escape sequence is the same as explainedin paragraph 6-16.

6-1_. ESCAPE BEFORE T_TVTOFFAFTER _3ILICAL DISCONNECTDuring countdownj there will be apprn_4mate_ 50 to 90 seconds between

time of spacecrafts unbillcal eject and time zero, which is two inchesliftoff. During this period, the three available methods of abort are:(1) _-e block house to missile hardline abort signal as explained in theprevious paragraph; (2) Ground c_.!_nd receiver abort signal; (3) Astronaut'sAbort Handle. _hese three methods all result in energizing the Mayday Relays.

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After liftoff, (Time Zero), there ere three methods by which an abortmay be _-_tiated_ _ey are: (1) Ground c_n_d receiver abort signalan_ (2) Ast_=._-,,tbort Handle, both of which were possible methods inthe prevlov_ _aph, (3) The Booster Catastrophic Failure DetectionSystem. _s +.bt_ method has been noneffective in the two previous para-graphs due to the _i TAme Zero Relay being de-energize_. However, _ _i

Zero Relay is energized two inches after liftoff and completes acircuit to the Nayday Relays if the Catastrophic Failure Detection Relayis ae-energlzeclby loss of power fron the missile.

6-16.When the Mayday Relays are energized, the abort sequence (See Figure 6-6)

will occur as follows: The abort Light on the left hand console will _33,--_-mate, the Spacecraft Separation Bolts Power Relay is energized and the Space-craft Separation Warning Light Time Delay Relay is energized. _e AbortRelay in the MA_--_n Altitude Sensor is energizes after Spacecraft Adapterseparation. _e M-_--_ Altitude Sensor com_utes the time delay required forthe spacecraft to reach a safe d_m-4c pressure before _ettisoning the EscapeTower. The Spacecraft Separation Bolts Squibs will be fired, releasing theSpacecraft-/_=pter _ Ring and allowing the three _4_4t switches to re-turn to their n_nal positions energizing the Emergency Escape RocketFire Relay, the Escape Roe_*t Fire Relay an_ the Spacecraft Adapter Dis-connect Squib Fire Relay, firing the Escape Rocket and the four SpacecraftAdapter Explowive Disconnect Squibs. _e Escape Rocket's 56,000 poundsof _ will _eparate the spacecraft frc_ the missile an_ carry it awayfr_n the sustainer at a mall angle. The Spacecraft Separation Sensor

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T_tm_t Switches also energize Spacecraft Separaticm Sensor Relays, whichturns on the green _ CAPSULE Teleli@ht 3 and also energizes the TowerSeparation Abort Interlock Latching Relay. The Abort Interlock Relayenergizes the Retro Rocket Assembly Jettisca Relay and fires the twosquibs of the Retro Rocket Assembly Jettisca Bolt. The bolt willfracture and the package will drop free of the spacecraft, beingassisted by a coil spring installed between the Heat _ield and RetroPackage Assembly for this purpose. When the spacecraft reaches a maxi-

altitude, contacts in the Maximum Altitude Sensor will close andenergize the Tower Separation Bolts Power Relay firing the bolts. Asthe three tower bolts are fractured, +_e segmented Tower Clampseparates allowing the *._ee Tower Ring Limit Switches to return totheir normal position energizing the Emergency Jettison and JettisonRocket Fire Relays. _ou@h these relays and their parallel contactsMain and Isolated Bus power will fire the squibs of _b_ Jettison Rocket.The tower will be Jettisoned clear of the spacecraft resulting in sepa-rating the two Tower to Spacecraft Electrical Discon-ects. _e separa-tion of either disconnect will de-energize the Tower Separation SensorRelays energizing the Abort Rate Damping Relay _ro,;_hthe contacts ofthe Tower Separation Abort Interlock Relay. _nls relay will send a sig-nal to the ASCS c-remandingrate damping until time of Main Chute deploy-ment. De-energizing the Tower Separation Relays will also stert two 2second timers in the recovery sequence. The first timer will arm the21,000 Foot Baroswitches and two seconds later the second timer arms the10,600 Ft. Baroswitches.

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6-17. ESO:'E ATZONThe methods of initiating an abort after staging are identical to

the methods named for the escape after liftoff and are: (1) Groundccemaandreceiver abort signal; (2) Astronaut Abort Handle; (3) BoosterCatastrophic Failure Detection System. AnY of the three methods _ "1]energize the Ma_l_y Relays. The sequence which occurs by the energizing

-of these relays is described in the following paragraph.

6,.18. OPE TZONThe signal which energizes _ Mayday Relays also is transmitted

to the missile tO shut down the sustainer engine (See Figure 6-7)._w0t_h contacts of the energized Mayday Relays_ a power circuit is can-plated to the ABORT Light on the main instrument panel and the .20gcontacts of the _h_us_ Cutoff Sensor are armed. As thrust decays to .20g,the contacts close and energize the Spacecraft Separation Bolts PowerRelay firing five Spacecraft Separation Bolts squibs and zeparating theSpacecraft Adapter Clamp Ring. The sequence following clamp ring sepa-ration is the s_ as the normal sequence (Refer to Paragraph 6-7). Re-entry may be accomplished by any of the emergency procedures (i.e., astro-naut or ground initiated). Refer also to Paragraph 6-9. If the abort isinitiated before the spacecraft has obtained the correct velocity fc_orbital flight and it is not desired to fire the Retro Rockets, the RetroPackage must be Jettisoned manually, it sh_,!d be noted that even if thespacecraft does not attain orbital velocity, the quickest way for re-entry is by _a_rgency firing of Retro Rockets.

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SECTION

SEQUENCE SYSTEM, LANDINGTHROUGH RECO VERY

TABLE OF CONTENTSTITLE PAutomatic Sequence Description ..............Automatic Sequence Operation ...............Emergency Sequence Description .............Emergency Sequence Operation ..............System Components................................

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vii. s imcESYSTmLAmminGm0UGHm covm z.. 7-m. AOmU TICSEQUm CE sc oN

_e _a-_4_ end recovery sequence system provides automatic electricaland mechanical sequencing to land the spececrat_t safely after an ab_ ornormal re-entry_ and to Initiate locating aids for assistance in the sub-sequent recovery. _e pr_mmry (completely aut_matic) system incorporatese drogue parachute, used initially to decelerate and stabilize the space-craft in the inttisl phase of recovery and a main parachute for furtherdeceleration. Redundant circuits have been incorporated to eliminate thepossibility of stng_e-point failures. The landing Is accomplished utiltz-Lug a 63-foot-dlsmeter parachute which is deployed at 10,600 feet. In theevent of a main chute failure, a 63-foot-diameter reserve chute may be de-ployed by the astronaut's m.anualselection. Both main and reserve chutesare reefed tO 1_m_t s_ock loads at initial opening. _he reefing line issevered autcuatically after a pradetermine_ time delay and the chute willopen ful_, lowering the spacecraft at the prescribed l-ridingspeed. Asouna f_ and ranging (SOFAR) b_ is attached to the main chute risersand is releaser as a function of main chute deployment. When the risersI_,_Itaut, f_e b_._ is ejected and falls to the ocean ahead of the space-craft. When the b_._ reaches a depth of 2,_00 feet below sea level, it isdetonated thus provla_-ga means for deter_-_ng the appro_m-te location ofthe spacecraft _n_,g area by soun_ fixing an_ ranging stations. Aftermain chute deployment, the landing impact bag is extended, providing acushioning effect for the landing impact. After impact, the ma_n chuteis autc_aticall_ disconnected followed by reserve chute ejection; how-ever, chute disconnect is delayed as a function of the Rescue Aids Switch:in autc_atlc (AbvfO),a 10-minute delay is accomplished; in manual (MAN), acue-second delay is accc_pllshed. _erefore, if the astronaut desires7-_


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t_medat_ chute meparation at 4.Tact_ he must positi_ the Rescue AidsSwitch to the "MAN"position at impact to by-pass the 1D-minute delay (atany portio= of the lO-_,_te _elay r_.4._._ after :Impact). _e astro-naut will _ egress no_a]__y taking with him the survival klt whichcontainsa 1_ee raft and other survivalaids.

7-2. A_TIC ._, OP_On rover separation, power is removed from the Tower Separation Relays

_he Main Chute SyltemArm 2-Secoz_l _J.neDelay Relays tO be ener-gized (See FA_n-e 7-i). After the 2-secondtime delay has run out pover_icws throughthe closed ecuta_tsenergizingthe Main Chute2-SecondTime Delay Relays, and a_ter a 2-second_elay arms the No. 1 10,600 ft.Baroswltchthroush+h. 10,600ft. Arm Relay cc_tacts. 5_e No. 1 and No. 2Baroseitches are _ired in seriesthereby requiring both swatches to be closedbefore normal m-tn chute deployment can be accc_lishe_, q_e No. 2 21,000ft. Baroswltohis arme_+_oush the closed contactsof the Main _ute Sys-tea Arm 2-SecondTime Delay Relays. Upo_ descentto 21,000 ft., both theNo. 1 and No. 2 21,000 foot Baronltches, which are wired in series,close_hereby energizing the D_o_e Deploy Rels_, _ the Drogue Chute M_Gar,deployingthe I_ Parachute. _he Drogue Chute stabilizesan_ deceleratesthe spacecraft. At sppr--4:_te_710,600ft., the 10,600 ft. BaromrAt_hesactuate the _,4. Deploy Relays resutting in the r_oval of the squib groundcix-euits and _ o_ all four squibs of the Antenna Fairing E_ect_r. Also,the Main Deploy Warai_ Light 2-Seconcl _,,,_ Dela_ Relay is ae_uate_, a_at the end of 2-seoc_l del_ the ze(1 Main Deplo_ Telellghtis l_--4--te_._he Antenna Fairing Sepeawtic_ Sensor ArmRela_ are energized _ the

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closed cc_ta_ts of the M_n Deploy Relays arming the two Antenna Fairi_Separatin_ Sensor Swi_es.

_e firing of _A four Antenna Fairing EJectc_ Squibs causes theAntenna Fairing to separate from the spacecraft. A la_Lrd_ co_nectedfrom the Aute--a Fairing to the Main Chute_ extracts the Main Chute fromthe chute c_ax_nt. The Main Chute opens _.Itla_ in the reefed con-dition to limit shock loads. Four seconds after the chute is deployed, thereefing 1t_e is severed by a pyrotechnic c_ge in the reefing lane cuttersalAowing the para_,_te to open _y.

_he separatic_ of the fairing from the spacecraft o!lows the AntennaFairing Separatlo_ Sensor Switches 1;o functlcn. _]_coushthe switches,power is routed to energize the Main Ejector Relay firing the Main EjectorBag Squibs. _ _ squibs fire_ _hey generate a gas_ filling the E_ec-tot Bag at the bottom of the Main Chute compartment aiding the e_ectton ofthe chute. At _he same time the Antenna Fairin_ Separation Signal Relaysare ener_Ize_ i1?,--_,atln8the _reen Main Deploy Telelight and re_ovi_power from the re_ telelight. Power Is also directed through the AutennaFairing Separatic_ Sensors to energize the Main Inertia S_rltchArm 12-Seeo_l Time Delay Relays. After the 12-seco_ time _elay has run out, theenergized contacts allow power to be supplied to energize the ___ding Ba_Extend and Landing Bag Naming Light 2,-Secon_ Tt_ Delay Relays as well asto the Inertla Switches. _he closed contacts of Landln_ Bag Extend Relayfire the squibs of the Landi_ Ba_ Valve releasin_ the heat shiel_1andextending the impact landing bag. As _ 2-secon_ time delay runs o_t,

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the Landing _ Ws_ Light Relay illmminates the red T_ndiD_ Reg

Telelig_ht. Upon heat shield separatlon, the Ianding _g Unlock Sig-nal T,_m_tSwitches are actuated and through its closed contact_ powerfrom the Auto I_ Bag Fuse is directed to energize the T_,_Bag Extend Signal Relay ill_ti_ the green Ta.A_n_ Bag Telelightand extinguishing the red light. _he force of impact on la_i_operates the T-ertia Switches which provide power to the coils of theImpact Relays. Through the closed contacts of the Yzpact Relays, poweris supplied to energize the Post Tal,w14._ _Sr_ Re.B _,_h theactivated contacts of the Post T_,A_,_ System Relays, power is tr_---mitred to energize the Impact Signal Relay. Also through the closedcontacts of the Post T_In_ System Relays, the Flashing RecoveryLight circuit is ccmpleted sett_n_ the light in operation. _en theImpact Signal Relay is energized, the green M_in Deploy and T_nd_,=Bag Telelights are exttnsulshed and the red Rescue Aide Telelightis ill-m4-_ted. With the Rescue Aids Switch in "MAN", at the endof the l-secoDd time delay, the Spacecraft Stabilization Relay is activatedallowing the Main Disconnect and Reserve Disconnect Relays to be energized;with the switch in "AUTO", this action is delayed I0 minutes. _ough theenergized contacts of Main Disconnect Relays_ the Main Chute DiscannectSquibs are fired, releasing the main chute from the spacecraft. _e Re-serve Disconnect Relays fire the Reserve Chute Disconnect Squibs releaetDgthe Reserve Chute an_ energizing the Reserve Deploy Relays. The ReserveDeploy Relays fire the Reserve Chute E_ector Bag Squibs. The Reserve

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Chute Ejector I_g Squibs activate the _s generator which has a one-second delay in ignition time before inflating the ejector bag ex-pelling the Reserve Chute and the dye _rker. When the Rescue Aidsswitch is placed in the "MA_" position or s_ter the 10-minute delaywith the s_tch in "AU_0"_ the Rescue Aids Switch Signal Relay and thePost Landl_ System Power Drop Hold Relay are energize4, q_e energizedRescue Aids Switch Signal Relay removes power from the red Rescue AidsTelelight and tll,_nates the green light. _e Post-I_ADg STstemPower Drop Hold Relay energizes the Post-Ta-dln_ System Power Dzop 30-Second Time Delay Relay. At the end of the 30-second t_._ delay the WhipAntenna Extend Relay is energized firing the Whip Autemm Extend Squibsactivating the gas cartridge exteDdl_ the active element of antenna toits full length. _hen the Post-EandAng System Re_ys are energize_ oniml_t and, depending on the position of the Rescue Aids Switch, power isapplied t-_4ate_ or after a 10-minute time delay to the coil of thePost Landing System Power Drop Hold I_ .,_-Io the Post I_d_ SystemDrop _0-Second Time l_e3a_r. After the S0-sec_n_ delay, the Post Iand_n_System Power Drop Relay is e_r_ize_ which removes power flwm the re-maining cmqnents except the WhipAntenna Extend aelay.

7-3._he emergency provisions of the _ system basle-_ ly consist of

-_.ually-operated back-up systems initiated by the astronaut. _e appro-prlate button, pu11-rin_ and switches are located on the Left Hand Con-

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-ANTENNA FAIRINGI "SOFAR BOMB

HF WHIP ANTENNAi' PILOT CHUTE LANYARD/ i

IE CHUTE RISER/

:HUTEHUTE

"" "_ PILOT CHUTE RISER

DEPLOYMENT GUN

/ RESERVECHUTE TO ANTENNA FAIRINGEJECTOR SAG

PILOT CHUTE lANYARDTO DEPLOYMENT

DY E

RESERVEPARACHUTE

PILOT CHUTE RISER

FM18-65

Figure %2 Main and Reserve Parachute System (Sheet 1 of 2)7-8


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CHUTE

ANTENNA

FAIRING _

SOFAR N3_/

DYE_RKER

FM18-65

Figure 7-2 Main and Reserve Parachute System (Sheet 2 of 2)

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sole. The emergency system controls manusJ__-tnittated _eployment ofthe Drogue, Main and Reserve Chutes, extension of the LsndJ_g Bag, andinitiation of rescue aids.

7-4-. msms OPZaATImOn descending to 21,000 ft., if Drogue Chute failure is detected by

lack of opent_ shock and _y a visual cheek through the window, the astro-naut will depress the I_ogue button (See Figure 7-3). Depressinghe buttonallows the Emergency Drogue Deploy Relay to be energized and the Dro@_eChute Mortar Squibs to _e fired deploying the Drogue Chute. If the greenMain Deploy Telell_t fails to t"!],,,.t--,t_, failure of the _nt Chute todeploy may be detected by a lack of opening shock, a visual check and nodecrease in rate of descent. Upon determining that the Main Chute hasnot deployed, the astronaut will place the Recovery Arm Switch on the Con-trol I_I to the .mmml position. If Main Chute Deploy is stl]_ notsensed, operating the Main Deploy Pull Ring energizes the Emergency MainDeploy Relay, firing the Antenna Fairing Ejector Squibs, ejecting theAntenna Fairl_ and deploying the Main Chute through the nor -_1 aut_-_ticsequence. When the green _4_ Deploy Telelight is ill-m_-ated and therate of descent is greater than 32-feet-per-second, the chute is vls,m_lychecked for damage. If the chute is damaged or did not deploy, actuatingthe Reserve Deploy _,11 Ring w_11 energize the l_serve Deploy Relays._yugh the energized contacts of the Reserve Deploy Relays, power isapplied to the F,_t. Chute l_sconnect fi_ the squibs disconnect___ thechute frc_ the spacecraft. At the same time, the Reserve Chute E_ectorBag Squibs are fired _nerati_ a gas after a 1-second delay and _n_4ati_the ejector bag which aids in deployiu_ the Reserve Chute.

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EMERGENCy _ DROGUE CHUTE

DROGUE DEPLOY MORTAR DROGUERELAy SQUIBS CHUTE

DROGUE CHUTE _41 _L_iL_T_" o_-L

EMERGENCY MAIN ANTENNA FAIRING J_DEPLOY EJECTORRELAy SQUIBS

MAIN CHUTE DEPLOYED BYTHE AUTOMATIC SEQUENCE

MAIN CHUTEFALLSTO DEPLOY

RESERVECkfLITEDEPLOY GUN

SQUIBSPILOT CHUTE

RESERVE MAIN CHUTEDEPLOY DISCONNECTRELAYS SQUIBS

RESERVECHUTEEJECTOR

MAIN CHUTE FAILS _IAG SQUIBSTO DEPLOY OR IS EJECTOR BAGDAMAGED

ELECTRICAL SLGNAL Ill!_ MECHANICALI MOVEMENTGAS INITIATEDEMERGENCY EMERGENCY

LANDING BAG LANDING BAGEXTEND RELAY VALVE SQUIBS

LANDING BAG

MAIN CHUTE

DISCONNECT ILANDING BAG SQUIBSFAILS

RESERVECHUTEDISCONNECT

RESERVE CHUTEDEPLOY GUNSQUIBS

PILOT CHUTE

I0 MIN. T.D. _ RESERVECHUTEEJECTOR BAGSQUIBSNOTE: RESCUEAIDS SWITCH IPCSITtONED TO "MANUAL" TO RESCUE AIDS I 30 SECJ .D. EJECTOR BAGBY-PASS "AUTO" 10-MINUTE DELAy. (10 MIN, T.D. RELAy) WHIP ANTENNASQUIBS

WHIP ANTENNA FMI8-66A

Figure 7-3 Landing and Recovery Emergency System

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Twelve seconds s__er the Main Ch_ is _p_j_ the greenBag _llght should be t_.md_a1_1. If the light d.oesnot cm_ on, pl_ethe Landing Bag S_Ltch in the "MAW"positions enm'Slzi_ the EuergeneT"Landing _ Extend Relay, f_rJ:S the l_-rgoncy Land_S BsS Valve Squibs,releas_ the beat shlel_ end _ the impact _ bag. Tenu_nrtes after _ the Rescue kLds Swtch By-Pass Relay is ener_Lzed._lhon aetlva'._ the relay by-passes the Rescue A_ds Swtch and enar_zes therel_m vhch mq_l_- po_r to fire the Math Chute Dsco_-et 8qulbs as yell.as "the squibs for the Reserve, Dseonneetj Deploy Gun, _ the _ector BagIn the mine a_ner as if the mritchwere place_l in the "MAN"position.

mo m_e 6rc_w parachute ass,._l.y (See Figure 7-5) eo_slstsof a eon_ea_

ribbo_1-t_ _ogue e_nop_ vitb _1%'ser, drogue _plo_ beg__ro_e mortar, sabot, aria &rogue mortar cover. _e drogue parachute cano-py 18 a conical ribbon parachute havi_ 8 gores of 2-1nch wlde_ l_O-lb.tensile strength ribbons on_ 8 tubular n_lon suspension lines of 1,(XX)-lb.tensile strength each. _ para_-te is constructe_ to a dl_eter of 6.85feet end per,m-entryreefe_ (restricted)to an efTecttve d_a_eterof 6.0feet by ,.e--,_ of pocket bands. The ccnst.w_te_ total porosity is 27.9%and the effectivepc_oelty (_hro_ ree_) Is 36.3_. _he 30-ft.Integralriser is made frcw three layers of 3,000-1b.tensilestrengthlow-elevation hot-stretched Daero_ webbing. _he drogue parachute stabtli-

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1 ANTENNA FAIRING EJECTORGUN 9 SHARKREPELLANT2 PARACHUTEDISCONNECTS(2) 10 DROGUEMORTAR3 RECOVERyLIGHT 11 WHIPANTENNA4 ANTENNA LANYARD 12 PILOTCHUTEDEPLOYMENTGUN5 BARDSWITCHES4) 13 PILOTCHUTE6 MAIN CHUTEAND SAG i4 RESERVEHUTEAND BAG

15 SEAMARKER7 EJECTIONBAGS{2) 16 INERTIASWITCH8 GASGENERATORS2) 17' SOFARBOMB.

J NOTEVII_V LOOKING INBOARDLEFTHAND SIDE

FM18-67

Figure 7-4 Landing and Recovery System Installation

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FMI8-68

Figure 7-5 Drogue Parachute

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1. "O" RING 5. CA_[RIDGE2. SABOT 6. CHAMBER3. INSULATION4. COVER

Figure 7-6 Drogue Chute Mortar Assembly

R3"IROTECT'VECAELECTR'CALCONN"C'O"_'"C"AMBER!ATTACHMET0B_"T_'N'"OR_'NOPL0_O0_BFMI8-74

Figure %7 Main and Reserve Chute Gas Generator

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__ma.a. SEDR 104

zes and decelerates the spaeeera_. _ canopy weighs 2..9 Ibs. wlthoutriser and 5.9 ibs. ine_ the 30-ft. Daero_ r_ser. The _c_e pars-chute deployaent bag serves a _ual function of (i) protect_ the drogueparachute _ eJe_ a_ (2) _ means_or order:_ dep1oymntof the &ro6ue parachute. _he bq is _A__eactlxred of cotton saracen fab-ric reinforee_l vith _1_ vebbing aria covered at the upper en_ vAth aheat insulato_of glass cloth. _he bag is weighte4 at the upper endvlth a 0.5 lb. lea_ &isc_hlch assistsin strippingthe bag fr_ the canopyat the c_.__leticnf 14.A and riser stretchout. Inside the bag arecotton tapes to v_4_h the riser is secured _uring packing in order to pro-vide orderly riser deployment. _he mouth of the bag is closed vith alight cott_ cord.

7-7. modus_ _o_ _rDS_SO__he _ parachute e_ectio_ mortar is a device for positive Ae-

ploy_nt of the drogue parachute _rAth sufficient ener_ to overe _ l_alpressure gradAe_ts an_ _avitaticnal forces. _he 4roL_e parachute ispacke_ in a protective bag an_ stove_ in _he molar tube o_.top of a_ASht_t sabot (See_ 7-6). :he sabot _me_ns as a p_s_ontoe_ect the parachute pack, when pressure_ i_ below by gases &_nera_frc_ a pyrote-_-_c charge. _ae propellant charge is _-ttial_ fire_ intoa breech eh..-_er of mall volv_e, to produce high pressure _nlch is sub-sequent_,7 vented through a small orifice sad into the main ,_-._er at rel-attve_,7 lover pressures. In this M--e_, reaction loads are kept to a.4.4,_._ since the pressure energy is not e_enAed instan_aneousl_. _he

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"_MO_NNE_. SEDR 104

pressure se:!4-u quality of the sabot is derived from an "O" ring, in-stalled in a _ve near the base. Two mall holes are located in _he "O"x_ groove to ve_t air _ra_ped in the mortar tube u_er_a_h _ sabot c_instalAaticn. For proper operation_ the "On ring and the inner wall of_ m_ar tube_ which Is always in contactwith the "0" ring, are _.-brica_e_ before installatic_. Be dro_w parachute pack is retaine_ inits et_ posltlcDvAthia _he mortar _e by a _ metal "Rene-_l"coverwhich is attached to the upper surface of _e antenna houai_, q_wee cut-out sectic_s_ provide_ in the sides of the cover, permit routing of thesteel cable risers into the drogue chute can. m_o cover is designed toconstrain the chute in its comp_t a_t negative decelerations andalso to require m_-_m-I forces to break loose from its attaohm,nts at thetime of deploy_nt.. Pressure of _he chute pack causes _he cover "to deflectin such a ma_r that atte#_t tabs i_,11o_t from _der attachingserevheads th_ a slotteAhole designedfor this purpose. _he ener_ requiredto expel the Aro_ue chute from its compartmentis provided fromhigh pressuregases, _enera_edby i_nltlon of a pyrote-h-_ccharge. _he cartridgeis1Oe_0___Ath 66 grains of powder, contained in a propellant can attachedto a steel bo_ _nich hooses the lgni_lon w_J_ anA terminates in aneleetrlcalconnector. Be i_nltlc_circuitryeomslats of two separateandIndlvIAualbridges, either of which is capable of ignitingthe power chargeupo_ applicatic_ of the proper current.

7_. MAINPARA__e main parachute assembl_ consists of: main parachute canopy,

riser, deployment be_, and parachute disconnect. _he main parachute

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Figure 7-8 Main Parachute and Packing Box

I , STRUCTURE 5. SHEAR PIN i

SHORTING WIRE 6. PISTON3] SQULBCA_RIDGE 7. LEADBUFFER4. BUSHING 8. ARM

FMI8-71

Figure 7-9 Main and Reserve Parachute Disconnect

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I 1. FIRING MECHANISM 4. SHEAR PiN II

IiI. BODY 5. ELECTRICALCARTRIDGE3. PROJECTILE 6. MA!NCARTRIDGEFigure 7-10 Pilot Chute Deployment Gun

FMI8-73

Figure %11 Parachute Ejector Bag

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canopy ls a 63-foot DRY4"-1 dtmeter rlngsstl type. _he rlz_sall para-chute ls fabrtcate_ from 2,25- and 1.1-ounce per sT,_e yar4 nylnn para-chute cloth into _8 gores with _8 suspension l_s o: _:_-poun_ tensllestrength. _he :-_- parachuteis pa_ke4 in a deploymnt bag -._h:J.ehpro-vtaem a 1_ sna_ force aria orderly aeplo_en_ (See FA_n_ 7_). _ebag is :anufa_tur_lfro: cotton sateenfabric,relnfcree4vlth _Icnvebbing an_ eovere_ a_ the upper end vlth _:erao1ex enA glmmeclothinsulation. _4de the be_, :i4n_ along its length,is a pair of trans-verse lockingflaps. _helr funetlcnIs to separatethe canopy fabrlefr_ possible _t v_Lth the l_-As and to eause full 11he stretch-cutbeforecanopydeploy.

7-9. P_ DZsc_Both main and reserve parachutes are att_rh_d to the spacecra_ by

a device designe_ to sustain the parachute loads during descent and todisc_-_ct _he pe_achute. _e chute is disconnected 10 -_w_es (+ 3. see-c_) a_ter _act _Ath _ Rescue Aids S_ltch in "_TO" o_ _ 8ecc_ afterpositioning the Rescue Aids S_Ateh to "MA_" (a_ter l_pact). _- ass_l_consistsof _ separatedetailsinst_1_l in a mounting _ure vhlch isan integralpart of the space_ra_t. _e parachuteriser is _ aroundthe am _hlch transal_sthe load to the structurethrcushthe plstc_. Theshear pin restrains the piston frc_ a_ _ion te_a4_ _o dAsplace tt._hen the chute _iscc_neetsignal Is ec_le_) a squib cartri4geis firedan_ _ resul_ e_pand_ gas fc_ces _- pisS;on fca_ard into the armrecess_ cuttlng _he shear pin :In the process. F.11 d.lsplaee_e_t of

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'_._Hmg.i SEDR 104,

pstc_ removes par_;;_e load. tranm_ssc_ to s_unture_ a_ theam to ro_e around, t_e pvot pin. _he loop of _he parachute riserslips off the arm end the disconne_ functo_ i8 ca_lete. _e lea&buffer serves to absorb e_-_gy of moving gst_ en_ prevents rebom_of _ p_tc_ back into the _ pos_v_.

_e reserve parachute assesb_y consists of: the pllot chute deploy-gun and _s p1_t para_ute I reserve parachute canopy_ reserve

parachute deployment bag_ en_ reserve parachute d_sconnect. _ reserveparachute deployment bag ls s4u_lA_ to the main pare_h_,te deploymen_ bagwith the addition of flaps st the upper ena of the bag to contain the_ p1ot chu'r,e, q_e reserve parachute d_sccnnect is Identical v'J.'__et used to dlsccanect the m_n parachu_. _he reserve parachute cauop_"is _entleal wth "the main pa_-_ute eauop_.

7-11. PILO_ PARACSU__e pilot parachute is a fl_; eircular type_ 72 inches in dXe_er

wth a 30 _. bridle. It is --.ufaetured at 3._-o.nce per square yawlfebrlo In the cauoP7 and 2.2_-ounce fabrlc :in the vanes.

7-12. cruz OTto

step :In T_ae seque__n_e of resez_e p_n'a_hute deplo_zent. Ei%her gas presst_eor ma elec'brtcal tzqp,_,,e _ cause the gun to fire, thus extmLli_ a 12-ot_ee ]pz'o_e_.-t_ile Idlt31 is at_aclze_ tO _Aze msez_e parachute pilot; chttte.

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_he pilot chute Inflates and in turn _,II. out the:reservechute, ccmpletlng the sequence. Whether fired electrlea_ or pneu-matlca_, a c_e-secc_d time delay is provided between receipt of the

end detonatic_ of the maln charge, q_S delay permits the ma4nparachute (if deployed and damaged) to separate frmt the spacecra__ toavot_L entanglmnent vAth the reserve parachute to be deployed. _ gunis basicall_ a tub-la_ body _nlch ccntalns the main firing eartridgeand the pro_ectile assmbl_. _e projectile ase_a_ly is held in placeby a pin which is aheare4 _hen the projectile Is expelled. _e main cart-rldge, which _nerate8 the gas pressure to eject the projectile, is firedas follmm: (i) Gas pressure, through +-_,. gas firing :ec_antm (s_pplle_when RESERVE PULL-RI_ is operate4), drives a fi_ pin into the primercap at the base of the ,.a_ cartridge, 4n4tlating a time delay train,causing a subsequent detonation of the charge. A m_,_m of 750 psi gaspressure is required fur pnemmatlc operatlcn. (2) An electric i_ulseis received at the time _ela_ igniter Install_ through the si_e of thegun. A_ter a c_e-secc_d delay, the igniter fires through the wall of themain cartridge and _etc_ates it instantaneously. Fi_ characteristicsof the igniter certrid_e are as follows: All Fire Current 2._ stopsperbridge, A]] Fail C_+_nt 0.5 a_ps per brtd_e, q_ i_nttton elrcutt con-sists of two indAvi_ual bridges termdnatin_ in a _-pln receptacle. _,_z_evelocity of the pro_ectlle is 250-300 ft/sec.

7-13.P .mm'm mmm, DO NOT INSTALL IN SPACECRAFT.

MAYtBE ACTIVATED ANDIUSED FOR _vO _POWER,SYSTEMS TESTS_ GROUNDAND BATTERY CHARGER TESTS.

VENT UNECONNECTOR

24V ON-OFF SWITCH'

OF F

[_EAGLE PI CHER MAR 4027C_ MAC 45-79707-17 (3000 WH)[_EAGLE PICHER MAR 4027-1, MAC 45-79707-13 {3000,WH)[_EAGLE PI CHER MAR 4027A, MAC 45-79707-17 {3000 WH)

_- _1_ [_> EAGLE PICHERMAR 3027C, MDE4587Z0-3 (3000 WH)

-24V 24V 24Vf _, 't FM18-3,_,Figure 11-6 Typical Battery Assembly

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__NNi/.J. SEDR 104

_',_,m capacity ra%ing of 3000 vatt-hours for the three main batteries,3000 watt-hours for the _wo stan&y bat_eries an_ 1500 watt-hours for theisolated battery. Each battery t8 equippe_ with 8 pressure relief valvedesXgned to mautA4- nternal preseure from 5.5 to l_t.9 p82. _he pres-sure x_lief valve XS moun_ed external to the battery ease. _e batteryewlteh i8 _ _he poml_ve 2_t volt CaLtput.

The battery electrolyte consists of a 40 percent solution of reagentgrwle potamsium hydroxide and distilled water and is used to activate thedry charge4 ba_x_y intial_y. After the first dAeeharge cycle, theba_ter]r may be reeharged by a constant current battery charger. Thebatteries fin_tsh power for all electrical equilment in the spacecraft;therefore, proper servicing and aLalntenanceis of extreme impca-tance._e ba_4res are desigl_d for five e m_.2ete cycles of discharge an8charge; however, for highest reliability, traits shoul8 not exceed foureyeles or an aetivate_ life of 60 days prior to flight. For the internalwiring of the batteries see Figure 11.6.

_he d-c "to a-c inverter8 installed in _he spacecraft are of asolid e_ate design cepable of operating continuously at i_,_ ratedpower output in a _ient a_osphere of 160F. or at 80F. at _ psia100_ OX_Ke_. _nverter8 are eoolec_ by the use of heat 8_nk8 and baffles.5he output is 32_ volts a-e + _%, single phase to ground, with a fre-quency of _00 cycles + 2. _ and essenti832y 8nusodal in _avefor_.

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Md_OONNmLA. $EDR104

Z.'L-Z3._-C_ 0-_0The a-e mm___er is located on the main Ins_nt panel an_ provides

the astronaut with an in_icstion of total current drain f_cm all bat-teries (.seeFigure ll-l). The basic _r movement has a 50 millivoltsensitivity. A shunt of suitable resistance is connected across theinput of the meter provi4ing a low resistance path to ground with theproper voltage drop at _0 amperes for a meter movement to full scaledeflection.

11-1_. _c vo_ o-_ v_A _-e vol_nster, and selector switch, are located on the main

Ixurt1_m__t panel (see Fig_we ll-l). Ap1_csctmatebattery cm_dltioncan be detez,m1,_dby placing _he D-C VOLTS switch to the appropriatepositions and rea_LDg the In_/vi_ual battex7 vol_es. Main and isolatedvoltages may also be determiDed by placing the D-C VOLTS switch to thee_propriate M or I position.

ll-_. A-CAn a-c voltmeter an_ a flve pOsltlon seleotor switch are mounted

on the main In_ panel. The five posi_lans of the a-e voltmetermrA_eh are 250 VA, 150 VA, Stay, ASCS ariaFANS. (See FAgusreIi-i).

ll-_. _u_ TTO_n_11-17. S_ST_ _S_PTIO_

Interior 1Aghtiz_ for the spaeecra_t consists of "two fluo_seonteabln lights, and a sez'les of warning telellghta. See Figure 11-7 for

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19C_D(PNNELL SEDR 104

I ' I, ' j (_t J Ss /',,_ MAIN INSTRUMENT PANEL,\

I

--. MAININSTRUMENTANEL

FMI8..32 A

Figm'e 11-7 Interior Lights and Warning Lights System

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NNELL SEDR 104

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'__NNJJ. $EDR 104

_catton a_l arransm_t of cabin lights and tele_hts.11-18. CABINFLOODL_S

TWofluorescent cabin flood l_hts are soont_ on brackets to ther_ght aria left aria above the astronaut. Power for the cabin lights issupplie_ fr_ +__ 119 V a-c inverter fans bus auA controlled by a threepositio_ s_teh loea_e4 on the left ec_eole. _he switch positio_s aremarkeA BOTH, 13' 0BLYe_l OFF. The cabin flood lights are of high actinicvalue; espeelallysuitable for ca_aerau_. _he lights produce littleheat and have a low Tattage cons,m_tion of 7 watts each (see Figure 11-7).

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SCT ION XII

COMMUN ICAT IO N SYS TEM

TABLE OF CONTENTSTITLE PAGSystem Description .................................. 12-5System Operation ....................................... 12-10System Units ........... . ................................ 12-30

1 2 - 1


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IVNELL SEDR 104

$ / t/ _ _

/

IIII

=

III

U

_z

N_

U

I\\

_ - , , -""_ _-_

Zi!k _ _ F/_18-I04

Figure 12-1. Communications Sequence

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8 8

i8_

If 'i

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__NNmi_. SEDR104

srenThe ss_onmt is pro_te_ vtth voice e_esttons t_h_t the

entirealssloa (see Table 12-1). A _ headset _ s__ eon-t_4_ vtthtn the utzoaant's heluet, ope_ste thzoush the Sa4to eentz_leircultsto the seleete4volee e_eatians set (see F_4ure 12-2). As_aeee_ intezl_ system Is av_41able_rior to _illeal easedlseoaneet.

receptlonis &vai_le t_ the _ Voiee _tlon set4arlag launch and orbit. HF voice trammm_sionms,y be +used,+,_sly afterspacecraftseparationby astronautselectionof the Z_ posltlon of the

sviteh. Th_ _ set is dAsabled at antennafalrlag separateaare-emergizedupon la_. The _ Voloe _eatloM set px_vldes re-eeptloaca4 transmission,du_ the post land_ ._1-e of the mission,_1-o.

reception is ava4_*_e t_t the entiremission by theVoice Co--cations se_ a_ its _ Booster_zTllfier. Traasmissioasover this set aa_ be mute _hen the _MPposition of the TBAI_MIT switchis selected by the sstrommt.

_e selectedtransmittermay be energizedby operatlonOf a _-_-+z_ nlteh, or by a voice operated re_ _e_ the VOX mrAteh is in theON _osltlonby speak_ into the z_lero_. _e _ trausmltter_

si_ml. _hls antc_atlefeatureI_ be ove_Ti_len_ the astro_t.

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NNELL SEDR 104

FMI8-102A

Figure 12-3 Command Receivers System

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_ _--_'_NmA_. SEDR 104,

A spaaecreftto llfe raft extensioncable is pre_ to a_aw theastro_sutuse of spaeeerl_ttra_tter-reeeivers 1_aileeL_mi4e the

ane_ aaaater_ attheeaaeZa _ lestext,mmlm__b_Le, _e_eeee_ en_ of the exteMioa,esl_e _ :]m_I_L .wt_ a _ _Leh Zlt,the ut_t's m_Lt _eo_eet. Wlth _e _ Switchin theposition,_ o_L _ _tton is pz_vt_e_. With the _ sw_h

_he _msn_ _elver pz_v_em an mers_z_r Sz_m_ 8tstton-to-_?aee-e_.vol_e ._mm_Leattons _ _h_ the autu_ untt_ s_aee-

h_aet. Power for die volee emmm_testtons sys1_ e Sure,Ledthro_ fuses _te_ iu the _eations _ _unle&tlens AS_ Fusewozae

A set of Reeeiver-_eeoder_and s_.tAlary decoder m_its is used forreception ana deeod_ of _una _aad ,_As. _hese st_aa_-arefor the purpose of a_tiv_ti_g various _ontrol circuits.

Power for the Comaand Receivers is s_pple_ th_Oa _e fuseslocated in the Cm_ations an_ _he Cem_mteations A_ Fuse Holders(see _'_ure _.-_.

_-._.A Tele_et_ Transmitter is px_ywided for _z_ie&tlDg _--tr_en_tion

iu_orm_tion to the _ stations. Zn_tion is picked up throughoutthe spaneera_ in the form of voltage_ _ voltage _ivi_er circuits.

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'_ONNL t SEDR 104

12-8


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__N_EI_. SEDR104

These voltages esuse VCO frequeneles to cha_e, to su1_l_r suitable in-puts tO the Telmtry Transmitter. (Refer to the T--truaentationSection. XIV of this mamutl). A trans_tter havi_ a power output of2.0 watts is usA_ for transmission of telemetry information. Theoperation of the transmitter is controlle_ by the T_TR_ sw_chon the Main Te-tru_ent Panel. It's _hree selections are ORRD COMDs OFF,and 00_. _he Ix_wer output of the telemetry transmitter is fe_ to eitherthe Main or the UHF Descent Recovery Antenna. Power for the system is

obtained frcu fuses locate_ in the Instrumentation Fuse Holders (see Figureaaa

ac0nsThe beanons provided in the spacecraft to aid trackt_ by

stations are C-Ban_ and S-Band beacons, a t_F Recovery Beacon and anauxil4A', 7 _ Bes_on energized at anten_ fairing separation, and anXF Recovery Bea_an_ energize_ upon landis. These besnons provide sig-nals c_tlble vlth _ection finding equi_ent use4 by the reeove_,crees. _he _Y Voice _'.;,----_tions tra-m4tter is keyed at anteanafairIDg separation to provide an additional signal for _1_ectioa finders.A flashing strobe liSht is lustalled for visual location of the spaee-crsf_ after landAng. (See Section VII of this manual).

Spacecraft power for the beanons system is supp]Liedth_ fusesloeatea in the C,_..,anlc&tions aria ASCS 1_ase Wolaez.s. (See Figure 12-_aaa

12..6._he voice _atlons, telenetry and beae_ receivers and

_m4tters, wAth their various frequencies and tTpes of out'pUts12-9


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__Nmg./. SEDR 104

require an antenna _stea _rAth vide ee_bilities. _aerefoze, fiveanteanasare used to fuAfillthe entire mlsslenrequlremmtsA Amain_ieone aucemm=a = ae_ .._=_e-_ _ Aut_m_._ u,.earot them,_Ior 1_o_ion of the albion. _ z_-e_zT, +.he Bteoae aatens .ut_e Jett_oaea to -_ov man lm_iutel ae_lo_mrC. _,e _ _le i. Jettisone4with the retro l_e. To zvA_laee.the UBF l_etion, a . . .

bicone separation Ul_n lsnd_, an HF ReeoverF _ Antenna an_ an Aux.

out the entire mission, C- ad S-Baa_ snte_as are provid_ for operationof the radar beae_as. Antemm _w_tehinKsndm_til_exi_ are performed==t,-,.ti_,y _ the_ =_=i_._ (see_='e= _-6=,d _-z3). _=rer_.acea on Use_e_ _w,_ s_A_-_e _eae_. (see T_m=e_.-_)

_-9. .a_:_ Cmm_A,= _ i i i r iiii i'_.. . .. .HF._ _ reoelver out_ are route# to the controlI_, _hls

ln'_rv'ides one _lmM_ e_tzol for _ m_,d.l.oand, one 'volume eontzolfor7

Of ecm_ aa:volee_"s:J.KI_I.8 1_ & iC_ pass filter,aa_ a_pllfleatlonof zem_].ting voice 8n_lx) is _ in the m_l.o ee_er. (Bee Figure 12-7)..

12-10


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_/


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/WO_OJwvmAJ,. SEDR 104.

Cn_4CsC.tcn Imd.l.osiSw_lJ f_nB the vo_ _,_-_ controls_ the 2nter-s,,_o fron the pscl.-4;o-the-p21ot She.81_,wmtones are sut_lAe8 to

the tape recca_er re_Ay and the two headset m_llflers in the _ocenter. "ae hea4set _2ifiers serve to smplAfy the audio signals and.fee_ them tothe indAvidual earlgwnes in the astranaut's helmt. _he_e-enerKi_l post_ten of the tape recorder rela_ _pplies al_h fo_receiver e-a',o 'to _he main 'tape recorder.

Z.xtto from +_J_._microphones _.s re& to two separate mieroph_e a_li-fiefs in the audio center. _aeoe two mplXfiers serve t;o m_p.Ltfy micro-ph_e o_tp_t to a level s_Aetent to s_P_V -,_,,_ _t_ circuits of _bevoice trans_tters, ghe nieropheue _pAAfAer output is also fed to the

energized by use of the Push-'_-Talk switch o_, 'the abort, handle. _ar.by+-_-VOX circuit _hen the VOXswitch on the _t panel is in the.'rnAaSNI"_poelt_cn. A_ter _.,Taot, .h. astrmaut -_.aAseonnee_ his ,uAtec_unleaticns em,_t_r an_ attach a _-he_am_-PTT mrltehasu_b_V to the suit ccmmm:tea't_ ec_ctc_. _s mlerophone-headsetasseub_7Is fit_e4vlth a 27 foot vaterproofelectricalieab_eand isused after egressto providethe astranautvlth tvo ray e_eatlo_sc_ the spacecraft_ and _ e_eatlcu systems.

IF12-11. HF _C_2ZC_S

5he HF voice eommnieattcaw set is an _ reeeiver-tranm_ter unit.

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A & " _! U.H.F. DESCENTANDRECOVERYANTENNA

__ _ ACTIVEELEMENT

" F ACTIVEELEMENT-ACTIVE ELEMENT

i _!'--ACTIVE ELEMENT _ / ["

" / [ IIIIr -''"NO / / ..... X I MAIN BICONICALc

I H.F. RECOVERY WHIP ANTENNA,

{clANDS-BANDANTENNA/_ ___"_\ 1.... _ _---,_,_ ,_.(TYPICAL3 ,LACES.) /__ ACT,VEELEMENTJ

_ (TYPICALOPPOSITESLOE) " FM18-116A:Figure12-6.AntermaS_m Utilization

:12-13


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_NNEg.L. $EDR 104

Power from the _ PreoYjpaet 2_ volt _-e bus is fe_ aireet_ tothe reaeiw m_,.ica of the set. Mac trans_Ltter is fed 2_ yolts throu_'_D' positlan of the _SKIT n_teh a_ the cloud contacts of

_arat.l.m _r, after _o,mrs_mc,a_m. ._m_Co 'to_ tz'ans-a l._tez"V.c_icm of the m l.t _Ls_ the ml.erolg_m m_-'2er in the au_l.ocenter. _he tr----_tteris keyea e_ther autma_leall_ _ the V0Xe_t _ _ _7 the utrmaut's use of _ xwh-to-_k _teh.(_ n_ _-8).

antenna ec_e'_1.en _rea the set :l.s b_ou_ _i,,,, .,.h.,,_ po_t_mIF _ SZLICT m_teh locs_ bel_ the i_h_Ju_ co.sole. _e

_RCT mr_ if_lizes kJaree positions s DIPOLE (orbit _Iv)_ BIOOHEe_d _P. MWsO t_ sw_eh po82tio_s _,vv_ opt/mt_ anteing* opera_0_.

o_bit. Au_Lo outlmt from the ree_wer_ _eln_uK li_eto_e dur_ trsns-ai.s_I.cn is routed to _ HIP_ol_e control _n the eantrol panel.

12-12. _MF V0I_ _SII_IICAT_IS

_e _F voice e_--_4eat2_ met is an N/_eee_ver-traum_t_r ,m_tdes_ned to operate m a frequeney of _ra_atel_ 299 Me. _he trenw_ttermrbput _s ineroas_ by a Npmmte _F booster _]fier.


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v _MCDONIIIELL SEDR 104'

12-17'


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_RNM;.I. SEDR 104

posl_to_ _ _he _ wl_ _ _o_the z_ee_ver Ne_i_theset..(See_ _-9). Power_orthe._tt_r seet_ o_*__.

iS also taken _ _ _ _OSi_vtoD of the 'J_/MA_'Y svtt, eh. Atbieone an_.e,_a Jepsz_i_ the bie_e _-psz_i_ z_ eon_aets asmme

a eont/w.c_ _ _ _ m' p=pous, r _tO _ tO the

the ,_,_4_oeem_r. _he _'anud.tte_" Is e_er_J.se_ ei+_-_' autnm'_I.eA!_yor maaual_ by the _. :It v:Ll.be ener_.sed, au_eBtle-,,y atbieo_e sepez_ti_ _o provde a IIHF'_ f_ _e_i_ _ equip-

the eeutr_l, lumel to the R/Y postt_.

coax 8_A_eh,a_ _tiple_or, a_ _he e_a s_i_eh to ei_he_ the

_ts_s_ voiceo't_++"e..eax,'e+t_,_ _ "P_ _w"aoae causes *.hebo_s_

pu_ is _ boo_e_ by _b_ _l.t_z to 2 n_s. _he booster iS _omU__b_e _er zaas4_, _ m_ttpzex_ ou_pu_seo_e_ t_.t_e e_ezu_ m_h '_0 et'k_r _ main bte_e _ _he _ rueue e_mua'JlmsOAoou.'k_tt :Px'oa _ reeeiver, lae_xllz_ s:Lcte'kcm.elm"l:_ _aumlssi_,is _ _o _ _' volume e_rol la the c_nt.x'ol l_seL.

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...._. 0 I_ _ 0 -- _ Z Z,..,

m z +z I_-_, _" I/_I-_I I',_Z FMle-II tA

:Figure 12-10. Command Receivers Data Flow

!12-19


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NNELL :_SEDR 104

TELEMETRY BICONESWITCH FUSE A m PRE- ANTENNA

t IMPACT

BUS MATININSTRUMENT PANEL24V

ANTENNA SWITCH

D-C (SWITCHES TO NO. 2ANTENNA FAIRING-- -- JETTISON)

ORND I'COMD 1 b )CONTOFF 1

TEL 2SWITCH 2

1[,_ EECOVERY 1

"_ KEY _ ANTENNA

iTELEMETRYCOMMAND(ENERGIZED TELEMETRY POWER TELEMETRY _TRAN SMITTER MULTIPLEXERBYGROUND SUPPLYCOMMAND) i

B-:-200V --! 2ILAMENT DVOLTAGE

GROUND 5

I 24V D_INSTRUMENTATIONi

GROUND TEST

,.GROUND TEST GROUND _ 1/2 SEC.TEST TIMEUMBILICAL SWITCH _ DELAyELAY NO. 3 RELAY

PM18-112

Figure 12-11. Telemetry System Data Flow

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L L

_c.elv_e.._.ecd_' unt_ eom,_._r_sf an IM reee_.ver. _he z_elve_s_nal asy be ,.__;,]-_e4 with s mztmm _ _Lx e_ s _oss_le' _ sudlo

_ea_les _hleh _ IaA:Lv'J.A,,a! e_'l_'ol re_. (Bee 1,_. 32-3.0).

m3.1,Telou4 cresol eh,,__ L _ea _la are 1='orlae4 _,, _ reee_L,rer-_o_r,vlth an -aa4+J.one]._ svallable In th_ --_11a_ 4eel. Cca-

ehsanel aesa=ets arenotcU.se3.oae. eason:.pae_ voice e_es'l:t_s _ be Ms4 _'m _ U,=mA st,at;tomtos_a_eeza_ _h "the e_ reeetwr, l_-e_.ve_"_s are s_e4_b_oUi_ a _11_ a_ _m_L_ler 1_ the a_l.o eeatez, etxcutts t;o .the astz'o-| t s I_. P .Oi.Oi.Oi.Oi.Oi.Oi_"| _ C_ila_ i_ tli _t_ _ _ ._t"

).8 vo)._ A-e bus. _ pover e_-'eults are roa_4. _ seet._.onsof

Ante_A t_U_ is _ _e bte_ae o_ _ _eseuasnta_,m-thz_h tha_ms svL_ an8 _ nu_t/_leze_ _o i_the _ecever.

M_e te_ t_It_er set Is an IM t.-_m1_e_ o_e=at1_ ca s

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_, 2,/,, 6=- - < :- _ : " ; . _ z _ = = _ = -

" Figure 12-12. Beacon System Data Flow

'12-22


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WCI_ON_mLL SEDR 104

Before _n_illeal drop, _h. telemetry tranmttter and its powersupply receive 04 VOltS d-c t_on the Ymtn PTe-mpact bus throt_h thee_er81zed Ground Test Umbilical Relay t nczmaZ_ open contacts. _h_ Sre]J_'s soZenold ts energzed +_,_h-'Ott_the ,__l]_cal until the ,m_i14caZ

To sllence _he _4 tra_4tter, the astronaut may place _he telemetrysvlteh In the OFF position whleh w111 prevent 2It V d-c power from reachln8the transmitter. PZaclng the telemetry mrltch in the ground c_andposltlcm enables a signal from the 8round to energtze the telemetryo.,_;_-_,,d relay vb.l.e.h will app.1_"power to the tranm_tter. _he elgnalls programmed to la_t _ mlnutes an_ then it is removed shuttt_ off thetelemetry _ans_tter. The tr_4tter wlZ1 r_,In off until c_=mndedagaln by _round c.-._-.-_._-e CONT posl_c_1Of _e _.w_3_/ switchappZies a_ttnuo_s power _o the _ +_-_-_ter.

Code_ Ins_taticn Inf_raatlon is m_pliea fro: the lns_w*utati_Ps_mSe _", aua usea to frequency _;:_,te _he tr_tter. (See _he_u_a_1oa Se_tlon XIV of thls :_usl).

BY power output Is re4 to the _ :nl%Iplezer where It is routedthroush the entm_- svlteh to +_-_e_-In"oiccme or _Y recovery antenna.

32-17. C-B_ BF_C_ he C-Bsn_ beaccm is a transponder _tt cc_lstln8 of 8 receiver and

tra-_4_ter operatu8 on a frequency of epprcnclaa_e3_ 5_00 to _900 MC._he beaccet ls _mbZe p,,l_ed and ls compectlble wlth modlfled FPS-16 r _a:-.Upc= ground c_ad_ throush the eo_an_ receiver, or by astronaut selection

1_23


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_O_NffLL SEDR 104

of the CONTpositiou of the C-Ban_ beacc_ switch, the beacc_ receiver isenergised. Interrogation by ground radar will then result in a eodearepl_ fron the beacc_ transmitter. Xnput power is from the main pre-i_act 24 volt d-c bus through the beacon relay conl;ro].l--_l by thecomm=_d receiver, or, for continuottsoperation_ throt_ _ C-Bandbeacon swltch. An OFF position of the C-Ban_ beacon switch is alsoprovided. (See Figure 32-3.2).

_e C-Band beacon antenna connection is %broach the C-Band powerdivider to the _ C- and S-Ban_ Beacon antennas. A phase shifteris used between the C-Ban_ Power Divider and one C-Bend Antenna %oprevent nulls in the raalation pattern.

12-18. S-_:._BN-_C05_he S-Ban_ beacon Is a transporter ,m_t co_slstlng of a receiver

aml transmitter. (_:= Figure ]2-]2). _he unit operates on a frequencyof approxtmate_V 2700 to 2900 MC and Is double _,_l,,,ed to reduos possi-bilities of unauthorized Interrogation. _his unit is ospatible withground based Verlo_t Radars and operates at a positive acceptancetolerate of + 0.5 mlcro-second_ sn_ a positive re_ectlon %olermace of+_1.8 _toro-mconds.

Power @rcute, interrogation and repl_ are the s_e as the C-Ben_kacon, e=ph

Beacon antenna connection is thro_h the S-Band Power Divider tothree "C" and "S" Ban_ Beacon antennas.

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_IIICDONNELL SEDR 104.

_z z_

12-25


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_MCDONItlELL SEDR 104

m,/m,TWo recovery beacons are eomb,-_t lnto o_e unit. One beacon operates

c_ hlsh frequency, whlle the other operates c_ ultra high frequency. Bothare energized to provlde radlo signals for recovery direction flnder equip-

Be HF recovery beacon operates on a frequency of apprn_m-tely 8 MCwlth a tone modulated output. It is powered by the 12 volt standby busthroush the t:pact relay end 18 energized upon landis. The RF power out-put ls fed through the rescue dtplexer _o the elevate4 HF Recovery Antenna.

Be _ recovery beacon operates on a frequency of approxlmate_7 243 MCwl_h pulse modulation. It ls powerea by _ 6 volt isolated bus t_lTC.,dh t_eantenna letting separation relay. _ht8 circuit is energtze_ when _ antennafatrtn8 ls Je_ttsc_. _he RF power output ls fed throush the aDten-a multl-ple=er an_ the anT_m-n switch tO the UgF rescue antenna.

12-20. _In_.T_ RES_JE_he Aux. Rescue Beacon operstes on a frequency of appr-_m-_el_ _43 MC

with pulse mo_balatlon. It Is powered by the 6 volt standby bus throush theAnt_--- Fairl_ Separatlon Relay. _hese cireulte are ener_zed at antennafairing separation. _he RF power is radlated frnm the Aux. Rescue Beacon_. (See ns_ 2-12).

12-2L AWTmNAS

12-26


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WOOONNILL $EDR 104

A bico_eal antenn8 28 used for pre-launch_ launch; orbit a_ 4n_tie2re-entry phases of "the________

ntenna fairing and is located over "the open end of tim recovery systemcce_artmemt of 'the c_lind_cel spacecra_ a_eterbody. _ bico_cal8ntenna serves 'the HF n,_ UHFvotoe receiver-transmt_ter8 s the c.--_,n_receivers, anti the telemetry trsns_Ltter8. _ ac_lve elemnt of thebioc_cal antenna f_s the upper portion o_ the antemm fa_r_ag _htlethe lover p_c_ of the fairing a_l the spacecra_ bod_ fm the groun_plane for "the ente_nA, (See _ 12-13).

A _ _ 28 used fca" the _ _Aee of re-entry; landingrescue. It; 2s a compact antenna located, cm the open eu:rtace ofmeovez7 syateus c_m_-_ent. The antenna 8 folded _en the m_;emmfS_T_ '_B :l.nfft._11*iL _ 8eCOolld8 8_ th_ f_ t8 ,_0'i_tt8C8_the UHF recovery antenna is erected an_ serves the t_F voice receiver.tra-m._t_ers,the UHF portion of the recoverybeacon, the _:--andre-ceivers,and the tele_etr_transmitter. (See Figure 12-6).

12_._. MAIN BICCffEBF D_I_OLBAHD _F RECOV_ _ F__he variousradio systa_ are ec_ to the blc_ne antenna,the

_F dipole or the U_F recoveryante--ain the follo_ runner: (See

12-27


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_MCDONNIILL SEDR104

(I) 'me HF voice receiver-tr_--m_tter antenna leads are ccmnectedto the HF _ SBLECT _ coaxial switch which _nen placedin the fo3.3.o___-_ positions feeds the antenna systems as fo!_s:(a) _ position, HF recovery ante--- thro_h the recovery di-

p]_xer.(b) BICUNE position, the bicone antenna through the main m_lti-

ple_er and the antenna sw_tch.(c) DIPOLE (ORBIT O_LY) position_ o _ HF dipole ant_ma on

the recto package.(2) _ O_ recelver-tren_qtter antenna lead is connected _ the

main w,1_Iple_er, _o the antenna nltch whose outputs feeds theblcene antenna un%il an%4_m_ separatlm. After antenna sepa-ration the descent anteDna is f_l.

(3) _e c_l receiver antenna lead is ecanected to the antennamultIple_er.

(_) _ Lov frequent7 tel_._ry transmitter feeds d_recltT to theantenna mtltip]_er.

m_he ant_"- _,_tiple_er enables aimcltaneous or i_I:Lv_Aual operation

of the ra&to system- using one antenna. EfTective_y this is a raalo f_e-_Cy _unction box v_tch allows several receivers an_ tr--_tters ooperate slmultaneously _hout Interference with each other.cc_nectlon o the antenna is e_h 1;he ente-na sw_tch to elthe_ _ae

12-28


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W_iI.L SEDR104

_iconlcal antenna, or the t_F rescue an$_-_na. _e antenna swi_.h isoperated by the antenna fairing separation relay to cause the autnmatlc_ht_t t_Cm _ main am_ezms to the U_ rescqze antemm t_c_ antemm

Jettlsm Figure

An antem_ Is provldml to permit _ radAo tra_eslcn and receptlo_a1_er ]_z_. q_, and_nna t8 a telescoping _ip an_zma vhloh is auto-matelal_ extended by a pyrote_ c after _mpact. Once extended, theantenna is uses for t_e HF voice recelver-tra_m_tter and the HF portionof the recovery beacon.

_he HF recovery beacc_ fee_s through the recovery dlplexer. _e HFvoice receiver-transmitter is fed through _ position of the ma_ ANT

and then into the zeeovery diplexer to the HF _aip ante---. _hedAple_r _ e_,,ltaneous or in_tvid,m_: operation over a single lead

12_._. C AND S B_D A_Z_ASm_ee C- a_l S-Bau_ antenna units are installed in _he spacecraft

structure f_r +_e C- a_ S-Ba_ beacons. _he_e ,,,_tsare equal_ spacedabout t_e ctrcm_erenee of the ec_lcal secttc_. _ach az_enna unit con-sists of one helix as a _-Ban_ antenna a_4 _ he_Y as an S..Bm_ _tenna.

_tenna lea_s from the C-Ban_ m_ S-Ban_ beac_ are _oute_ through_ i_vid_el pca_r dividers tO the three assoclate_ he1_- onte--as. (See

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_ONNBCA. SEDR104,

An HF Dipole antenna is used while in an orbit conditlon. _hedipole ante--- consists of two unitsj one attached to either side ofthe retro package. _he active e_ts co_Islstof tubular bery11'h,,_.copper ribbons. _e ribbons are rolled in a flat condition prior toorbit. Upon reaching orbit, a squib is fire_ on the dipole antennasaasa_lies, to release the active elements and allow them to unroll andbecome tubular in an extended cc_Ition (See Figure 12-13).

12-z9.12-3o.A io

_e audio center provides transistorized audio s_pliflers, a voiceoperated rela_ (VOX), an audio filter, tape recorder control circ,xltryand transmitter control circuitry. (See Figure 12-7). All componentsare contained in a light weight, foem encapm, l_ted --_t.

Two fixed gain headset _plifiers are used to bring audio signalsep to headset level and feed the headsets separately. Two fixed gainsmplifiers are provide_l to increase the dy,=_c microphone outputs toa level suitable to be used with the various transmitters.

A low pass filtar, with a cutoff f_ frequencies above 3000 cps,filters the audio supplied fr_ the c_ receivers. Outputs fromthe filter is fed to a variable gain_ command audio amplifier.

_e "voice operated relay" is a translsturIzed s_pllfier with separatea_ustable threshol_ level and release time controls. _e amplifier

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_,mqCJ_NNEI,,L SEDR 104owrates a relay to provide a grounding circuit for tranm-ttter keying._his --tt parallels the external PTT switch.

_he auaio center fur__a_s a circuit to appl7 the keying grom_potential to _e transmitters. Each circuit is protecte_ from therest by a diode.

A relay is installe_ in the audio center for suppling pover an_audo signals to the tape recorder. In the de-energized conditl_, therelay closes s circuit to the tape recorder input, thus audio receivedby the spacecraft is recorded whenever _nRtrumentation pro_cmas taperecorder operation.

When the microphone svitch or VOX is operated, the tape recorderrelay is energised if VOX operation of tape recorder is selected. Oneset of closed relay contacts nov c__ple_s the recorder power circuitindepen_ent of instrumentation l_c_raw_nS, _nile a second set ofcontacts routes signal from the microphone amplifiers to the recorder

The circuits in the audio center operate directl_ from the space-craft 24 VOlt d-c i_puts with no further re_tlatton or voltage increase.

The audio control panel pruvdes controls and circuits for the audiosignals of the variotts spacecraft receivers (see Fi_tre 12-7).

The HF and I_Y circuits are routed through individual T-pads tovol_ne controls. _e _F circuit has a single vol_ne control, the stoneis true of the _F circuit, _htle separate vol,m- control is provided

1 2 - 3 1


298/365

_NItI|LL SEDR 104

for the cm--_ a,_o circuit. Fxed l_uts are used for the alarmtone and groun_ tnterphone circuits.

_he panel also contains a mrl_ch override f_ the impact keTlngfeature used with the _HF tram_tters, mzt _TInK butt_ on the panelto _nt_,_ ___e tel_etry B+ s,ppl_ to provide ezer_ keyl_. (P_fer

:12-32. HF VOI(_ _vr,_-__he _ volce _t s _- _ receiver-tr_ttter de8_ as a mall,

The receiver sectionof the --It 18 a translstca_r_di,_t_mecircuit using a crystal filter,crT_al diode deteeta_ an_ elaH B audioemp!tt_er. _he final au_to amp]J_er i8 use_ for sift(me du_ lw_-a-assic_8.

_e tr_--._ttermetlon of the unt ut_ vaomm tube s_s fo_the crystal ontro11_ oscl]._atc_, driver an_ power m_.llfer. _aepower mplfer m_ be mod_]_l_l up t_ _0_ by a tw--_tstm_LNd _eohempl_er aml motivator. __q___seu_l.o ert,_8 are alao _meclteL- e_le-tone. Tr_-_t_ter output i8 _ watts. _ae _m_ i8 powered by spacecraft,21_volts d-_; Power is route_ _ an exte__-_ mr'r_.h_ contacts

+_" __ _ a_ _ _ _ r _t _

power, rela_ operati_a and a t_an_istar_ poee_ea_verter.

12_32


299/365

"__NmLL SEDR 104

D-e voltage i8 also _ from the receiver RF stqes. AutennaswAtchtng is acec_llahe4 by 8 solt4 state circuit ihich block= the:m_.ver _ trensaJ.ssJ.oa.

vtxl,ee _eelvar-t,r_m,ma,t.tt,_r ecaas:l.st,of an _ reee:l:ver-'taem_s-:ttter designed as a malls 11gbtwet_ ,s,_t operating near 297 Me._..,_-._tt;er _ i8 .5 va_. 51m traasmAtter _ is boosted oya flnal boo_e_ _IACAer.

_e receives aectloa of the _t is a translst_ised sul_0_ete_dyaeelrcalt_ a crystal coatrolle_local oscillator,c_ fA1t_r _crystal _Alcde4erector, _he audio sexton o_ the re_elver also servesas _e speeeh _llfler, modulator_:d px_ldes s14etc_e fc_ the trans-:i_te:. _he transalttersectlc_of the ,,-_tutilises a _-ystaleon-trolle4 o_l_-tcr, trl_ler ea_ p_nr _m_iAfler. _he RF se_tlc_usesvacu=n tubes _hile the mo4.ulatlcu clrcultsare transistorised.

Spacecraftpover, 2_ volts _t-e,Is m_iAed to tbe.se_, m_s vol_a_eis applAed to th_ _e_etver_ a_Ao circuits en_ back _h.rou_ am externaltrl_s_Lt seitch to an internal po_er ec_e_er. _s transistorizedconverter supplAesB+ vo_e to "the transmitter RF se_ttou. _b_ems-_Ltter fil_ent voltap is also a_lle4 bT the externeA transit s_Atchca' the bteone se_a_'a'tlas, ml.a_ _ bieone separaticm,

SWAtehln__ receiver to transaitter operationis aee_,_.l,t.abed__e_ _ potentialis appliedto a s_itehingrela_ and a blo_circuit. _ _1_ _z_t4es sn_ m_l,.power eo'uve_c,x" mrteh_.bloek:L_ eireult z_oves reeever voltage,


300/365

_mNJ_L. SEDR 104

A booster smq_r Is usea prior to _ to increase the . 5 'nttou'_ut of the _ tr-,,_t'-t_n" to 2.0 w4_ts'. _he higher power is alsoavailable after lsn_ng.

_snaz _ to the _,oos'_ is route_+.h__uShaoubzepo_, exe_throw coaxialrelay. _en the relay is de-ener_zed, the Signal is route_

_ e _ k .

_e eo_ receiver-decoderis a transistc_-izednit cc_slstingofan FM Receiver an_ a decoder unit to operate control e_reuits.Cs__ng..-.e-_o).

receiver se_tic_ of the ,m_t is a _ual eonversic_ st_he_circuit. _he first local oscillator Is crystal con_n_lled a_l uses twostakes of f_equeney _ttpleatton. Two stages o_ _m14_eation are usedfor the" f_rst IF, 78 MC s_na_ _e sec_ loea_ ose_Uator ts alsocrystal ccntzolle_ _ wAth the first XF _ glv_ a resultant secon_IF of.lO. 7_ MC. Outputi_o_ the IY strip18 +.-_o_h li_Iterto the _18-

"cz_uator. _;;_o mm_l_flers boost the 41se__m_-to: output for_he corn-voice,-,--__ .u_ a_oaor_-,_ver.ae_ver tn_m-neupp_ese

ten _eeoderchannelsin _e aet._e In&i_i&ml deceder _--*la each provide filters f_ $_elr _pecli_lc

e_ frequency an_ e_la_ers to operatea _o_ble pole,_ouble +_rowre1_r for ee_h_,,.,.,.,-I..5_ tenrel_'_ _huesakeavat_b_eno_a1_aria normal_ _ ebntaeta for extea_aL eoutrol e_at_; operatteu.

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S_eeraft po_, 18volts_-e,is_ to pawer_he set. A_ioae elx_t, vA_In the _.It, is _ for voltap regui_ion.

auxili_ _e_oaer operates vi_ _e recelver-_eeod_r _mLt, al-

he deeoder _s_nels _ the e_IAa_ deco4er are laentleal to thedecoder -_m_is of _he reeelver-_eeo_er, _i_ the exeeptioa of thee_ fze_a_lesat _MA_ they_era_e.

_he _;elamtoe_" l_3_er _lles pne_a_e vol_age _ _il:,be "be3.e_et,.-_

e_a_ _tc4ss. 81u_eers_ X_,r, 2_ volt, _L-e,s all,ted to a _-aus-

_.

A i_1! _ave, ex,j_ _io_e reeti_Aer iS _ Ca_ one oeeo_, .YAthvoltap _e_,_-ti_,to_ovlde200volts_-c..m4mof apize_,,-_.v 2.0 n+..tst ap_ox_a_e:_v _ _C. a_hetraao_e.er s.an I/( ua_ u,_ WO _m_s _a _rme_ta_m circuits, wo"st_us_are epp_L to a_Lr_ step sS4pa_ m_Aer-ioola_o_ c_-_Lt. _ 1_'.

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_MODOItlNItLL SEDR104

portions of the transmitter consist of a triode quarts line oscillatorinto a pentode buffer stage feeding a triode power smplifier. The VCOsignals are fed to the oscillator stage. Filament and B+ are obtainedfrom a separate power supply. Spacecraft 24 volts d-c is the telemetrypr_,_y power supply.

_e C-Band transponder is a pressurized superheterodyne receiverand pulse modulated, 400 watt peak output tran_itter, operating in thefrequency range of 5_O0 to 5900 MC (See Figure 12-12). With the exceptionof the _gnetrcn an_ local osc_l_=tor, the ,,_t is trs_sistarizea. _ereceiver consists of a pre-selector, local oscillato_, _00 MC IF _nplifierstrip, pulse c'Lete_or, p,,_-e--T.lifierand decoder. Resonant cavities areused for the pre-selector and local oscillator.

The tran_,_tter section accepts decoder outputs andpulse mod,,Intesthe transmitter out-put.

The unit contains a power supply for converting spacecraft 24 volts d-cinput to filtered 2_ volts d-c and regulated, 115 and 150 volts d-c out-puts. Antenna sharing is through an internal diplexer.

32-. S-m DThe S-Band transponder is a pressurized superheterodyne receiver and

pulse moa,,1-tea;lO00 watt peak output transmitter operating in the fre-quency range of 2700 to 2900 MC. (See Figures 1,?.-32).

12-36


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_ _O_N_. SEDR 104

Receiver and transmitter circuits ere _he same as "those used in theC-Ban_ beacon wlth the exceptlc_ of the pre-selector, local osc_11_tcran_ trAn_tter which are designed for S-Band frequencies.

_e recovery beacc_ cnm_ines an HF_ to_e m_lulated_ 8.36_ MC trans-mitter an_ a UHF_ pulse modulated_ 243 MC traumnitter into one .m.11_foam encapsulate_ _mit. (See Fi_tre 12-12). _e _F section of "thebeacc_ is a c_e tube circuit wlth a p,,lp.e codi_ network. _heHFsectlc_ of "thebeacc_ is a "transistorizedcrystal oscillatc_ _ "twostage power mw_l_fler vlth t_e mo_ulatic_ supplied from a power con-Verter. _e beacc_ utilizes 6 exu_12 volts d-c _m the spaceereftpower syste_ _e _F secttc_ is energize& by e_plying "the 6 volt _-cto a transistcrize_ power cc_verter. A i_,11wave, crystal diode elf-cult is used to rectify the power converter ou_ which is applied tothe UHF stage. ApplFin_ 12 volts _-c e_ergizes the _F sectic_ of thebeacon. No power converter is re_-_recl f_ the 12 volt !,,!_t.

Modulation f_r the _' section is provide_ by ro_tlz_ the 12 volts_pl_ tO _he power e_lifier sta_es throt_h a secon_._y _ of thepower converter.

12-_. At_Vv_Y _F RESCUE BEACC_AND AFf_NA_he Aux. U_F Rescue Beacon, consists of a pulse m_lula_d trans-

mi_ter and power supp_V which is enclose_ in a foam encapsulated case.(See _ 12-12). The unit _s c_ecte_ to the 6 volt standby busan_ has an output of 91 watts. The on_enna is moonted in the recoveryc_mpa_nt add is self erectlc_.

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_MOOONNELL SEDR104

antenna multiplexer allows reeeptlcn end tr_nm_ssion of themany spacecraft frequencies over one l_e to _ _Icone or U_F recoveryantenna. _he unlt consists of a n_er of filters a_=Aen6edso that allspacecraft frequencies between 15 and 450 MC can be multiplexed on thesingle feed iane. Each input channel is provlded 60 db of isolation.

_e recovery diple_er n-It is used for the _F voice recelver-tr----mltter and HF section of the recovery beacon. One low pass and onepass filter is used to diplex approximately 15 MC on one feed l_-e to theHF recovery antenna.

RF mrAtehing is ace_wp1Aahed with motor driven SPDT swatches._pllcatlon of spacecraft 2_ volts d-e through external circuits drivesthe svltch to the appropriate RF position and opens the power circuitfor that position. The manual HF A_ select switch is hand positionedto the DIPOLE - BICCBE c_ Ww_P position.

12-_6. BICO_E_he spacecrai_ ls electrically divided in two sections. (See Figure,

_-6). _e antenna fai_Ing structure at the Junction of t_ese sectionsresembles a discone antenna. _Is Junction is center fed by a coaxialcable from the c_mmwlcatlons sets. At frequencies between _ and 450MC the a_enna fsi_In_ _ts _Ike discon_ ante_a, A lower frequencyof 15 MC causes the u_It to resemble an "off center fed" dipole_ betweenthe upper end lower _ts.

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_' _C_NNBA_t. SEDR 104-

_us the bicc_e antennamay serve alI spacecrafti_requencleaslth_he excelTtlo_f C- and S-Bands,a_ receptlcnend transmissionwlthln 14m4ts of the spacecre2_system.

_'_7. BI00HE ISOLATORAn isolato_ is proviaed to shield electrical wires _hat pass +.h_.ough

_he blccne antennafairing structure. _2e Isolatoris formed into a tube_ch is eurve_ to a'l1_ mount:l.ngbeneath T-heperiphery of the ante_-afairing.

12-._he _Y Dipole Antenna is extended to 13 feet, 8 inches after an orbital

.... conditionis reache_. Selectionof this antennafor _F use is s_hlevedbythe astronautthroughthe use of the HF AHT _LECT switch locatedto "therlShtof theastronaut.(SeeFAsure12-6)

12-_-9. trm_zm_'_ _ rmoo_mm_Be U_F descent and recovery antennatakes over the D_F functions

of the bic_ antennawhen the antennafairingis _ettisc_ed. (SeeFigure 12-6). _e U_F descentand recoveryantenna is a fan shaped,verticallypola_izedmc_opole locatedc_ the top of the recoveryccm-part_ent

Upc_ landing,impactcircuitsinitiate a sequencefor the HFrecoveryantenna. (SeeFigure 12-6). _'_eelevated antenna acts as avertical_vpolarizedm_nopole for BY frequencies.

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_O_NNmLL SEDR104

iz-51.9-Am) AW m AS h_ee antenna --_ts serve the C- and S-Ban_ beacons. (see

Figure 12-6). Each ,m_t consists of a C- and a S-Ben_ radiator.Each _dlatar is a eavt_ moemted,helix antemna.

12-52. Nn_xARy UHF _e_E BEACONA_NAA spring-tape type antenna is vertical_ mounted in the recovery

compar_J_t an_ is connected by coa_l cable a_ec%_ o the auxiliary_F rescue beacon inside the spacecraft. _lth the btcc_e entenna In-stalled, _he tape antenna Is held in a bent position an_ _on bicaleseparatic_ the an_n-a sprlngs into operating positio_.

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SECTION Xlll

NAV IGATIONAL A IDS

TABLE OF CONTENTSTITLE PAGGeneral ................................................. 13-3Navigational Aid Kit ............................. 13-3Satellite Clock ........................................ 13-3Altimeter ................................................... 13-4N_4__:':_'_::::: ::_ Longitudinal Accelerometer 13-5_IilH_IHIHIH_ ...................

...iiiiiiiiiiiHiiii'iHii_._ii!iiiii_Attitude-Rate Indicator 13-5_iiiiii_ili_iiffiffi_iiiiii_;;;i;i_ ..........................__:_:_:_:_:_"-__ Navigational Reticle .............................. 13-6::::::::::::::::::::::::::::::::::::::::::::::::::

"ff.:ff:":''"L:ffL:.::._:.:L:'.:'_fff_ffffff!_ff_:_:::::::::::::::::::: ::::::::::::::::::::::::::::::::: :::::::::::::::::::::::::::::::: :::::::::::::::::::::::_i_iiii_ii_ii!iiiiiiiiiiiiiiiii_iiii_iiiiiiiffi_iiffffiNff-___..:!!!!!iiiiiiiiiiiiiii_iii_i_!i!i!iii!igiiiiiiiiii_i!!!_:f-N.-='_.::::::::::::::::::::::::::::::::::::::::::::::::: ::::::::::::::::::::.'._{_!ii{:H:_:i.:iffi:'i{:HL:{-:'ff-:_'H''''"::'!ffffff_ff:Z:_.:::::::::::::::::::::::::: ::::::::::::::::::::::::::::::::::::::::::::::::._i{_Siiff-[ii:iiH{{iHHiff'ff:ff:'H!!'!{_'!_'ff":_":":'.:"_":""-::ff_..:!i:{{iHi!i'ii:i{'i{iiff_"f_i"HH-_'ff:'!'!{":":L:.::.ff.:fffffffffffffff_.' iii'!! iiii!i!iiiiiiiiiiiiiiiiiiiiiiiiiiiii!iilWiiiiiiiiiiii ':"::_:. iiii_iiiigi!!iiiiiiiiiiiiiiiigi!g!!_gi i i i i i i i ! i 3

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_ONNELL SEDR 104

(TYP.)

_E T IM E R ES ETSATELLITE CLOCK

/1

=%LNAVIGATIONAL

AID Kl'f _

_ PENCILHOLDER

BINDER ASSEMBLYF M18-5 4 A

Figure 13-] Navigational Aid Kit and Satellite Clock

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'_ _'_;Nmi_.. SEDR I04

13-i.Imr_atlau_ a1_s Vhleh are x-_ct_ to o_ts_ al_ttw_j ec_wNs

w1_,1_y an_ _ _ are prc_r1_ to aCt_Lu 8wL ,.*4?taln thea_"_tu_ th_c_h each _ of *_ _-_h_.

_-_. __AL A_ I__e nav_a_cml ect4 klt ecmslsts af a neopx-_m_eoa_ n71xm ease_

_w_ s b_le= asse_r; ew_ Is nount_ _ the nsln 4n,r_me_(see _ 13-].). _ b4_-r 8ssmbl]r ecuststs c_ a mmb_ c_ h_Sexear_s, l_me_ ho_a-_"t =_'b-.,Jea_ 1_meJ-_ sn_ _ (2) _i_ z_,_m_xtons_d_s. Mw I_ _ ea_s are us_ to _ note ear_s_ cheektsts t _ esz_ _ navJ4_tlcms_ _s as x_q_.x-_ _ the sl_ac_-c_'s_t Etsslcm. _,' 1_ne11 ho_ _s _bz_ea_ _ neoprene eoa_an_ Is sewn _o the ease. _te _-_s_ 3_twxL_ls seemed, to the _ass,=._y by roans of a _m z_,_ntla_ s]_, A uean_ _a x_t_nt_ca

seemms _ b_u" 8sse_y to the _ eoa'l_l n_'lm earn.

2he =_,el"_Jtee:t.oe.ks _ e.l.ee'l=.o-me,,t,=,rlea.l.-t:tm.'L_1_'tee ].oeate_l.mthe _ rJ_bt o_ _gw =stn hurla_ l_z_L _ sate].l.tte eZoek _,,,t_=tes

s]_h_ _ve= watch, _ =un=utl._ wou_ watch ls h=eate_t _n _ tWJperZet=t-hewd.eoz_w_ of the sste_ltte clock. 2_IW3_(M L_ _W _08_1 _ _ is _ts_le_4 _ 4J41fltsl 4rm eouxd_s. _he _ eoun_,sh_Leate _ _,, _ _, sn_t _. _he _ e_ts aow ht c_ step

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_Hm=.=. SEDR 104

teleM_ht. _ t,_1.e.14_ht is _ate4 in ___ _ r_ht-ha_ eox-=_

_)= _ is _t_Lstea te_ see_,, _r1_ to x_,ro_a_ t_,w..M_ sste]31te e]_J is au__-=tleally stazd_4 by 28 1;'D-C pmm_at 1t1%=o_. _0-1_ thls not oecv_, a mrLtehlsbele4 _ Z_O is prov14e4s_eve =ha _a_=t to _h. _ to _ the a=-_-_ to ene_l_Lze_eeZoe.ksat mamLmml._ta_ ssaso_). '_= :_zoi_-sa=t_Je _ n_,=_T

hsma_ _.atea _a the :Lower=d_ht act'the __!4+.e e:Loek_e _:l_y setthrough the e,_-,,_ x.eeelvex-s. _ -_tes _to: to _etz_aa= ttw,the satellite e3_ck t=_l_Lts s stsnal to the _.to start h_u_seamers ol_wat/n_ ec_hmmwZ.V and.sssuzesrate Syro o_erat_o_ In _re-_rs_lm _ _ se_aace. Whenret_c_ _Lme is obtatne4_ a set .of eoutaet _tnts v_th/n the eloek e_e, tntt_attng the _ =e-

the eabi= t'J.oo_lAKhts.

z3--_.. _,T_T'..__e sZtlaete_ ls a l_:essuz'e sens:t_l._e @s_leeloeate_ o= the 1owe:

le_ of the m_tn _t _el (see Seettm ZZ _or _-___tloealm).5he s_lLttuetez'i_l.eates the external presm_.re (in ]pcxm_sper s_uaz'e_h a_so::l=te]_.&) _ the s,l.t,t"l;c_(t= _,houast_ of feet) above sea

13-4


311/365

___fm. . SEDR 104

level c_ the spaeeersft. Mae statle systm _s the ataosldmr'..epresma'e n_es_ for the a1_. l_ Is a sh_terevolnti_ _,cat, rater _a 0 t.o 100,000 f4_t, vlth a _r at I0_000 f_r_ (_WI)

aceelercmet.er lh_e.h 18 1oeat._1 o_ _ u_mr ls_ of "the_,rumen_ _ (see 8e_icu rr fc_" _ lae_toc_) _ss _3.f-e_un_Lta_L is housed Ins he,nm_ien!"ty sealed e_elosvze. 2he seee_is 4estsne4 to tn41este aeeeJ_-a_ton in _he range -9 to 0 _o 21 g _lts(1 S _"J_ is e_,-_ to an seeele=at_an of 32.2 feet Per see_ 1_ _ea_).Attached to the face of +..___+eeelercmeter are three pointers. Oneln_lea_es lnstan_eous aeee_ezatlc_. _ _ two polnt_s are

1_d_,ers. _e _oz7 _t_ _eeo_4s _ost_lve seeeXa=s_tc_ _other aeac_ potnte= ln41eates negative acee_zstton. _he since7 lx_zb_sIncorporate a ratehe_ device _nleh maintain a deflection unit _he sawresetI_ aeaus of a reset knob .,,_.r_,hs _oes_4 _n the lov_ left headoc0mar of the aeee_.

Attltu_.e-Ra'te _g_I.eatcn' Is a "dn'ee wcLs _ .ratesad at'_d.tu_hs_Lea_ wj_c_n locate4 s_prax_wte_y at _he top e_ter of the m_Ln__ _enel (see Section IZ for exact location). _e syst_ _Le_tesp:P_h_), z'o__ _ yaw angles am1 _ ra_es. The u_L_ is a ecm_t_eaz_mlim_t eemd.s'c_ c_ a x_te l_alesto_ s:otma _.eh am post"btcme4sroll a'_,d._;u_e Incllea_mr) a _ at_.tude In6eatoa" sndt a p_eh a%'f_L_e

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__Imt J. SEDR 104

Indicator (see 8eet:Lcn XI). Mae rate lndlestcr dlsplsys three pointers._e ra_e of _ _ _ieh is flat lhlte in color is parallel tothe pon_w at _he z_LZ att_ae n_oat_w. _ z'st_ _ :raw pon_rwhich s yellow ._a eo.l._ ls po:tn't_, tawax'ds the _.- attltu4e ln_Leato_.q_e rate of pith l_M_ter _aleh is pink :Ln colo: ls _ towar4s thepltch attltu4e tn41cat_. _he system ecmpcmm_saz_ c_lete_y lnt.er-_able so _ _a41._e of one c_caent shal_ not necessitate :e-callb_atlca or :epla_xt of the ent/ze systea. Mae attitude-rateln41cstor is aetlva_ by pitch =a_e, _ rate and yaw rate _ans4_ers.Bach t_ is i4entlealan4 eonsls_sof a g_-oseope,ampli_er an_ ade_t_. _hese eau_eats fun_ti_utcsetherto pz_xtueea 4-e _,_ _,=_:eaal _othe_ rateof chenseof a_7_ae.

13-7. wavma_c_ n:zcrz_he navlKatienz_ele is a devlee_hlch d_s _hea the space-

crs_ is at t_e eozreet aa_e to= z_wo _J_e. I_ is locate1 at _he rearto the _ _ t_e _'s _,,_ (see _ 13-_). _e na_-

Satm _le is aomt_l _ a 180o_ (frm _ to rlSht), thisallows the _ to be poslttou4 so nat _,o block _he vle_ to theast_'s _ _ s_111 be secesslble. 5_e ins_ _hen it isIn _s vlewble posS.tA_ncontains t/nted red l_htln_ systea o_ suffl-

four (_) flues are vertleal. Maefourth _,,- _aleh is hm_J.soatal is theline _aleh ls ze_dA_4 _o be t_ to the esz_r,h_ _o z_z_ l_e._e _A_ht_ ,_sta _ auta,e_ea_ _ _'_,henthe_stnuna_ _8_t_tr_sve4_e_en. _w S=eadaS3A_ n,_be dAumaby t_euseoZa po_-

1_-6


313/365

rt_ICDONNELL SEDR 104'

ELECTRICALCONNECTOR

WINDOWRETICLE

NORMAL ATTITUDE/ \

(RETROGRADE ANGLE) /

PITCH ATTITUDE YAW ATTITUDE ROLLATTITUDE

(PITCH UP) (YAW LEFT) (ROLL LEFT)

(PITCH DOWN) (YAW RIGHT) (ROLL RIGHT): FMIS-14&

Figure 13-2 Navigational Reticle

13 -7


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_WNm- SEDR 104

o14 l'_1.ter. _he 1_.ite:" Is ol_zate4 by :o_at_Lag the c_s14e o__i,,,rtmm_t _Lch _ W_7 the 11Sht intensJ.t_'.

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SECT/ON XIV

INSTRUMENTAT ION SYSTEMS

TABLE OF CONTENTSTITLE PAGESystem Description .................................. 14-5System Operation ..................................... 14-5System Monitoring .................................. .14-6System Instrumentation Control ............... 14-30Instrumentation Recording ....................... 14-33System Units ........................................... .14-36

i i i i i i i i i i i i i i i i i i i i i i i i i i i i i i i i i i i i l i

14-1


316/365

>-

i ..i m_

FM18-140-I

Figure 14-1 Instrumentation Component Location-LeftSide (SheetI of 3)

14-2


317/365

14-3


318/365

_MCDONNELL SEDR 104

/

FM18-140 3

Figm'e 14-1 Instrument Component Location (Sheet 3 of 3)

1 4 - 4


319/365

"_/_NNffLL SEDR104.

mmmmmmmm ,z.The _--_entstton sys_ consists of the _Jor c_ents shown

on Figure I_-I. These eo:ponents coupled wlth various tz_--_cers andother plcln_ devlees provlSe a means of monlt0r1_ the physlcsl condl-tlon and reactions of _e astronaut as well ss spaeeez_ft eondlt_nssad systems ope_tlonsl pe_ozmsnce. This dsts so obtained Is applled

_ur1_s vol1_e eont_olled subeaZTler osellla_rs which mo_nlates theLow-Frequency Telemetry Tz_nsmltter and rsdlates %o ground ststlons forenalysts and ew_uatton; this s_e data is also recorded on a tape re-corder in _he spacecraft for subsequent stu_7 and interpretation.

A portable 16 mill_meter cram is provided for the sstz_ut torecord on film _ar_us events of interest during the mission. Prowlsionsare also provlde_ for automatic pro_:_ed control over so_e componentsnot intended for eont_mous operation.

1_-2. S_ST_ 0PERA_0_The _--trumen_t:h_n system is auto_t$c and eemi-au_/m-_tc in opera-

tion r_ the time power is e_plled to the spacecraft until 10 minutesafter landia_ _paet, ho_ev=r_ certain components may be controlled orinterro_tted &ar_ fl_ht by either the astronaut or _ e---_._. Thet--tru_en_tion system is di_ed into _k_ee LToups_ n_ely, monitorl_,control and reeordi_. These three groups are treated _tvi_,*_ly in

14-5


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_MCDONNELL SEDR 104

Instrtmentatton monitoring consists of sempllng values of pressures,temperatures, conditions and operations of various u_ts and functionsthroughout the spacecraft. (See Figure 1_-6). These samples are con-vetted into signals composed of voltages proportional to the te_erature,pressure and conditions being measured. The proportional voltages arecalibrated within c_n _=ximm and mini_m ranges to provide zero andf-!l scale reading. Instrumentation monitor_-_ is sub-divided into twoareas nemely, High Level and Low Level. A description of each is providedin the following p_phs.

(o- vHigh level input signals are chmmele_ into the c_tator (elec-

tronic switching device) which is located in instrumentation pac_=ze A.The coNmutator continuously samples its input channels, combining thesi_ o_-1 voltage l_,l-es into a pulse train from the c_tator. This l_u!setrain (PAN) is e_plied to a 10.5 _C voltage controlled subcarrier oscillatorwhere the cha

Documents

Project Mercury Familiarization Manual 20 Dec 1962